US2393604A - Bomb stabilizer - Google Patents
Bomb stabilizer Download PDFInfo
- Publication number
- US2393604A US2393604A US475341A US47534143A US2393604A US 2393604 A US2393604 A US 2393604A US 475341 A US475341 A US 475341A US 47534143 A US47534143 A US 47534143A US 2393604 A US2393604 A US 2393604A
- Authority
- US
- United States
- Prior art keywords
- bomb
- stabilizer
- missile
- trajectory
- angle
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Lifetime
Links
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B10/00—Means for influencing, e.g. improving, the aerodynamic properties of projectiles or missiles; Arrangements on projectiles or missiles for stabilising, steering, range-reducing, range-increasing or fall-retarding
- F42B10/02—Stabilising arrangements
- F42B10/04—Stabilising arrangements using fixed fins
- F42B10/06—Tail fins
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B25/00—Fall bombs
Definitions
- This invention relates to means for improving the ballistic performance of elongated, symmetrical bombs or missiles dropped or projected from aircraft, or projected from smooth bore, unrifled, weapons, the chief object of the invention 'being to improve the stability of such bombs as will be explained with the aid of the accompanying sheet1 of drawings, wherein:
- Fig. 1 represents a bomb provided with the improved stabilizer of this invention, in perfect vertical stabilization
- Fig. 2 shows the same bomb turned from its true trajectory due to influences which the improved stabilizer is designed to rectify.
- Fig. 3 is an end view of one form of the improved stabilizer
- Fig. 4 is a side view of the improved stabilizer of the radial type
- Fig. 5 is an end view of Fig. 4.
- a bomb or other missile is said to be fully stable in iiight when its longitudinal axis is tangent to its trajectory (the path of motion of its center of gravity); in the case of a vertically-falling bomb, whose trajectory is perpendicular to the horizon, the longitudinal axis would be coincident with the said perpendicular. This is the condition of the bomb shown in Fig. 1 wherein the center of gravity is designated I0.
- My improved device makes use of the very factors (partially listed above) which disturb the stable night of the bomb or elongated projectile, to return the bomb or elongated projectile to stabilized condition.
- I attach at the rear or tail end of the bomb or elongated projectile a stabilizer 20 in the form of a short tubular member spaced to provide a clearance A.
- the tubular stabilizer 20 may be held by a number of radial fins 2
- the tubular stabilizer 2l has, at all pointsbeing, in fact, a figure of revolutionan airfoil cross section, similar to the cross section of an airplane wing.
- the chord a/-b of the airfoil stabilizer 20 is parallel to the direction of relative airflow, i, e., the angle of attack (between the chord and the relative airflow) is zero.
- the chord makes an angle of attack (s) with the relative airflow resulting in the creation of a drag (D) and a lift (L).
- the improved stabilizer may comprise a tubular member 20, Figs. 1, 2, which may be of circular, square or irregular shape.
- a square-shaped tubular member 30 is shown in Fig. 3, held in place by radial ns 3l extending from tail ring 32.
- Figs. 1 to 3 are polygonal figures of revolution.
- the principle of the invention is applied to stabilization of the radial type in Figs. 4, 5 where the radial lns 40 have airfoil cross sections, and extend from the tail ring 42. While four radial fins are shown in Figs. 4, 5, it is clear that the invention is equally adapted to three or more radial ns.
- a device for stabilizing the flight of an elongated missile having a reduced tail end by maintaining the longitudinal axis tangent to the trajectory traced by the center of gravity, said missile having radiating fins attached to its tail end, arcuate stabilizers connecting said ns, said stabilizers being tapered in longitudinal crosssection and positioned with blunt ends toward the front end of themissile and having a camber comprising convex surfaces facing said reduced tail portion of the missile and concave surfaces facing away from said reduced portion, said stabilizer presenting an angle of attack with the axis of the missile and beingadapted to coact in ght with the air flow through the fins and ,create a torque tending to turn the tail end of the missile in a direction to decrease the angle of yaw from the trajectory to bring the longitudinal axis of the missile into coincidence with said trajectory.
Landscapes
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
Description
Jan. 29, 1946. w. F. BERGER BOMB S TABILI ZER :Filed Feb. 10. 194s l l a alla gmc/who@ William FI .Eerder www atented Jan. 29, 1946 UNITED STATS am OFFICE Application February 10,
1 Claim.
(Granted under the amended April 30, 1928;
The invention described herein may be manuactured and used by or for the Government for governmental purposes without the payment to me of any royalty thereon. n
This invention relates to means for improving the ballistic performance of elongated, symmetrical bombs or missiles dropped or projected from aircraft, or projected from smooth bore, unrifled, weapons, the chief object of the invention 'being to improve the stability of such bombs as will be explained with the aid of the accompanying sheet1 of drawings, wherein:
Fig. 1 represents a bomb provided with the improved stabilizer of this invention, in perfect vertical stabilization;
Fig. 2 shows the same bomb turned from its true trajectory due to influences which the improved stabilizer is designed to rectify.
Fig. 3 is an end view of one form of the improved stabilizer;
Fig. 4 is a side view of the improved stabilizer of the radial type, and
Fig. 5 is an end view of Fig. 4.
. A bomb or other missile is said to be fully stable in iiight when its longitudinal axis is tangent to its trajectory (the path of motion of its center of gravity); in the case of a vertically-falling bomb, whose trajectory is perpendicular to the horizon, the longitudinal axis would be coincident with the said perpendicular. This is the condition of the bomb shown in Fig. 1 wherein the center of gravity is designated I0.
Various factors and conditions such as the relative air flow passed the bomb, cross-winds, eddy currents, different atmospheric conditions such as air temperatures, unevenness of the bomb surface, lack of symmetry in its shape or weight distribution, etc., tend to cause the bomb to turn on its center of gravity, which continues on the perpendicular trajectory, various angular amounts depending upon the magnitude of such disturbing forces. The bomb is shown in Fig. 2 in this unstable condition, having been turned, by said forces, on its center of gravity through the angle shown (the angle of yaw, the turning of bomb being known as yawing).
My improved device makes use of the very factors (partially listed above) which disturb the stable night of the bomb or elongated projectile, to return the bomb or elongated projectile to stabilized condition. For this purpose I attach at the rear or tail end of the bomb or elongated projectile a stabilizer 20 in the form of a short tubular member spaced to provide a clearance A. The tubular stabilizer 20 may be held by a number of radial fins 2| extending from a ring 22 of the improved stabilizer secured on the tail end l2 of the bomb.
1943, Serial No. 475,341
act of March 3, 1883, as
The tubular stabilizer 2l) has, at all pointsbeing, in fact, a figure of revolutionan airfoil cross section, similar to the cross section of an airplane wing. In the stable condition of the bomb (Fig. 1) the chord a/-b of the airfoil stabilizer 20 is parallel to the direction of relative airflow, i, e., the angle of attack (between the chord and the relative airflow) is zero. However, in the unstable condition (Fig. 2) the chord makes an angle of attack (s) with the relative airflow resulting in the creation of a drag (D) and a lift (L). The latter force, which is at a lever arm (m) from the center of gravity l0, creates a torque (of magnitude, LXm) about the said point in a direction (clockwise, in Fig. 2) tending to bring the bomb back to stable position (perpendicular, Fig. l) As the bomb approaches the vertical, stable position, the angle of attack decreases; hence the torque tending to continue its turning also decreases. As a result the bomb will seek the vertical position as the point of equilibrium,
The improved stabilizer may comprise a tubular member 20, Figs. 1, 2, which may be of circular, square or irregular shape.
A square-shaped tubular member 30 is shown in Fig. 3, held in place by radial ns 3l extending from tail ring 32.
The improved stabilizer'of Figs. 1 to 3 are polygonal figures of revolution. The principle of the invention is applied to stabilization of the radial type in Figs. 4, 5 where the radial lns 40 have airfoil cross sections, and extend from the tail ring 42. While four radial fins are shown in Figs. 4, 5, it is clear that the invention is equally adapted to three or more radial ns.
\ I claim:
In a device for stabilizing the flight of an elongated missile having a reduced tail end by maintaining the longitudinal axis tangent to the trajectory traced by the center of gravity, said missile having radiating fins attached to its tail end, arcuate stabilizers connecting said ns, said stabilizers being tapered in longitudinal crosssection and positioned with blunt ends toward the front end of themissile and having a camber comprising convex surfaces facing said reduced tail portion of the missile and concave surfaces facing away from said reduced portion, said stabilizer presenting an angle of attack with the axis of the missile and beingadapted to coact in ght with the air flow through the fins and ,create a torque tending to turn the tail end of the missile in a direction to decrease the angle of yaw from the trajectory to bring the longitudinal axis of the missile into coincidence with said trajectory.
WILLIAM F. BERGER.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US475341A US2393604A (en) | 1943-02-10 | 1943-02-10 | Bomb stabilizer |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US475341A US2393604A (en) | 1943-02-10 | 1943-02-10 | Bomb stabilizer |
Publications (1)
Publication Number | Publication Date |
---|---|
US2393604A true US2393604A (en) | 1946-01-29 |
Family
ID=23887148
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US475341A Expired - Lifetime US2393604A (en) | 1943-02-10 | 1943-02-10 | Bomb stabilizer |
Country Status (1)
Country | Link |
---|---|
US (1) | US2393604A (en) |
Cited By (11)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2459357A (en) * | 1944-03-30 | 1949-01-18 | Philco Corp | Bomb fin structure |
US2584826A (en) * | 1946-05-31 | 1952-02-05 | Gulf Research Development Co | Aerodynamic surface for dirigible bombs |
US3015269A (en) * | 1958-12-19 | 1962-01-02 | Jr James H Potts | Stabilizing fin |
US3341152A (en) * | 1957-09-27 | 1967-09-12 | Avco Mfg Corp | Means for and method of controlling attitude of re-entry vehicle |
FR2353824A1 (en) * | 1976-06-01 | 1977-12-30 | Rheinmetall Gmbh | LIMITED RANGE PROJECTILE |
US4147124A (en) * | 1977-09-26 | 1979-04-03 | The United States Of America As Represented By The Secretary Of The Navy | Apparatus for launching stores from a submerged vehicle |
EP0210732A1 (en) * | 1985-06-27 | 1987-02-04 | The State Of Israel Ministry Of Defence Rafael Armament Development Authority | A balistic body stabilized by flexible fins |
US6297486B1 (en) * | 1996-10-09 | 2001-10-02 | Rafael Armament Development Authority Ltd. | Base drag reducing device |
US6644587B2 (en) * | 2001-02-09 | 2003-11-11 | Tom Kusic | Spiralling missile—A |
US20050224631A1 (en) * | 2004-03-05 | 2005-10-13 | The Boeing Company | Mortar shell ring tail and associated method |
US10890422B2 (en) * | 2007-07-26 | 2021-01-12 | Scarr Research and Development Co., LLC | Ring airfoil glider with augmented stability |
-
1943
- 1943-02-10 US US475341A patent/US2393604A/en not_active Expired - Lifetime
Cited By (12)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2459357A (en) * | 1944-03-30 | 1949-01-18 | Philco Corp | Bomb fin structure |
US2584826A (en) * | 1946-05-31 | 1952-02-05 | Gulf Research Development Co | Aerodynamic surface for dirigible bombs |
US3341152A (en) * | 1957-09-27 | 1967-09-12 | Avco Mfg Corp | Means for and method of controlling attitude of re-entry vehicle |
US3015269A (en) * | 1958-12-19 | 1962-01-02 | Jr James H Potts | Stabilizing fin |
FR2353824A1 (en) * | 1976-06-01 | 1977-12-30 | Rheinmetall Gmbh | LIMITED RANGE PROJECTILE |
US4147124A (en) * | 1977-09-26 | 1979-04-03 | The United States Of America As Represented By The Secretary Of The Navy | Apparatus for launching stores from a submerged vehicle |
EP0210732A1 (en) * | 1985-06-27 | 1987-02-04 | The State Of Israel Ministry Of Defence Rafael Armament Development Authority | A balistic body stabilized by flexible fins |
US6297486B1 (en) * | 1996-10-09 | 2001-10-02 | Rafael Armament Development Authority Ltd. | Base drag reducing device |
US6644587B2 (en) * | 2001-02-09 | 2003-11-11 | Tom Kusic | Spiralling missile—A |
US20050224631A1 (en) * | 2004-03-05 | 2005-10-13 | The Boeing Company | Mortar shell ring tail and associated method |
US7262394B2 (en) * | 2004-03-05 | 2007-08-28 | The Boeing Company | Mortar shell ring tail and associated method |
US10890422B2 (en) * | 2007-07-26 | 2021-01-12 | Scarr Research and Development Co., LLC | Ring airfoil glider with augmented stability |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
US2393604A (en) | Bomb stabilizer | |
US5439188A (en) | Control system | |
US3603533A (en) | Spin stabilized ring-wing canard controlled missile | |
US4351503A (en) | Stabilized projectiles | |
US2835199A (en) | Stabilized self-propelled missile | |
SE8600812D0 (en) | AIRCRAFT WITH UBERKALIBRIGEM LEITWERK | |
US3964696A (en) | Method of controlling the spin rate of tube launched rockets | |
RU2722329C1 (en) | Missile | |
US3790103A (en) | Rotating fin | |
Youn et al. | Numerical study on bending body projectile aerodynamics | |
Chadwick et al. | Interception of spiraling ballistic missiles | |
US3333790A (en) | Aerodynamic roll control mechanism | |
US3015269A (en) | Stabilizing fin | |
ES271926U (en) | Training projectile | |
US3016827A (en) | Aerodynamic roll control system | |
US3384326A (en) | Aerodynamic strake | |
US4170330A (en) | Weapons system | |
Maikapar | Bodies formed by the stream surfaces of conical flows | |
US3311376A (en) | Off-set tow target | |
US2984181A (en) | Wedge cruciform fin | |
USH932H (en) | Projectile fin | |
US3611930A (en) | Spherical shaped body with aerodynamic torque ribs | |
US2943568A (en) | Stabilizing device | |
RU2799901C1 (en) | Supersonic missile | |
RU2358233C1 (en) | Guided projectile |